US9115650B2 - Ring gear mounting arrangement with oil scavenge scheme - Google Patents
Ring gear mounting arrangement with oil scavenge scheme Download PDFInfo
- Publication number
- US9115650B2 US9115650B2 US14/293,279 US201414293279A US9115650B2 US 9115650 B2 US9115650 B2 US 9115650B2 US 201414293279 A US201414293279 A US 201414293279A US 9115650 B2 US9115650 B2 US 9115650B2
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- US
- United States
- Prior art keywords
- gear train
- oil
- oil collection
- epicyclic gear
- collection feature
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/04—Features relating to lubrication or cooling or heating
- F16H57/042—Guidance of lubricant
- F16H57/0421—Guidance of lubricant on or within the casing, e.g. shields or baffles for collecting lubricant, tubes, pipes, grooves, channels or the like
- F16H57/0424—Lubricant guiding means in the wall of or integrated with the casing, e.g. grooves, channels, holes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/027—Arrangements for balancing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/28—Arrangement of seals
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D1/00—Couplings for rigidly connecting two coaxial shafts or other movable machine elements
- F16D1/06—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end
- F16D1/076—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end by clamping together two faces perpendicular to the axis of rotation, e.g. with bolted flanges
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H1/00—Toothed gearings for conveying rotary motion
- F16H1/28—Toothed gearings for conveying rotary motion with gears having orbital motion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/04—Features relating to lubrication or cooling or heating
- F16H57/0402—Cleaning of lubricants, e.g. filters or magnets
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/04—Features relating to lubrication or cooling or heating
- F16H57/042—Guidance of lubricant
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/04—Features relating to lubrication or cooling or heating
- F16H57/042—Guidance of lubricant
- F16H57/0421—Guidance of lubricant on or within the casing, e.g. shields or baffles for collecting lubricant, tubes, pipes, grooves, channels or the like
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/04—Features relating to lubrication or cooling or heating
- F16H57/042—Guidance of lubricant
- F16H57/043—Guidance of lubricant within rotary parts, e.g. axial channels or radial openings in shafts
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/04—Features relating to lubrication or cooling or heating
- F16H57/0458—Oil-mist or spray lubrication; Means to reduce foam formation
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/04—Features relating to lubrication or cooling or heating
- F16H57/048—Type of gearings to be lubricated, cooled or heated
- F16H57/0482—Gearings with gears having orbital motion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/04—Features relating to lubrication or cooling or heating
- F16H57/048—Type of gearings to be lubricated, cooled or heated
- F16H57/0482—Gearings with gears having orbital motion
- F16H57/0486—Gearings with gears having orbital motion with fixed gear ratio
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/08—General details of gearing of gearings with members having orbital motion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/70—Slinger plates or washers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/34—Balancing of radial or axial forces on regenerative rotors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/40—Transmission of power
- F05D2260/403—Transmission of power through the shape of the drive components
- F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
- F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/98—Lubrication
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49462—Gear making
Definitions
- This invention relates to a ring gear used in an epicyclic gear train of a gas turbine engine.
- Gas turbine engines typically employ an epicyclic gear train connected to the turbine section of the engine, which is used to drive the turbo fan.
- a sun gear receives rotational input from a turbine shaft through a compressor shaft.
- a carrier supports intermediate gears that surround and mesh with the sun gear.
- a ring gear surrounds and meshes with the intermediate gears.
- the intermediate gears are referred to as “star” gears and the ring gear is coupled to an output shaft that supports the turbo fan.
- the ring gear is connected to the turbo fan shaft using a spline ring.
- the spline ring is secured to a flange of the turbo fan shaft using circumferentially arranged bolts.
- the spline ring includes splines opposite the flange that supports a splined outer circumferential surface of the ring gear.
- the ring gear typically includes first and second portions that provide teeth facing in opposite directions, which mesh with complimentary oppositely facing teeth of the star gears.
- a turbine engine includes a fan section including a plurality of fan blades, a turbine section, and an epicyclic gear train coupled between the turbine section and the fan section for providing a speed reduction between turbine section and the fan section.
- the epicyclic gear train includes a plurality of intermediate gears.
- a carrier supports the plurality of intermediate gears.
- a sun gear meshes with the plurality of intermediate gears and a ring gear surrounding and meshing with the plurality of intermediate gears.
- the ring gear includes first and second portions that each have an inner periphery with teeth.
- the first and second portions of the ring gear have an outer circumferential surface opposite the teeth that provides a first thickness, a second thickness greater than the first thickness and axially inward from the first thickness, and a flange extending radially away from the axis.
- the radially aligned portion further includes a groove operable to allow oil to pass through a connection between the radially aligned portion and the flange.
- the groove is at less than or equal to a 45 degree angle relative to the flanges.
- the groove is at an approximately zero degree angle relative to the flanges.
- the oil collection feature is an oil baffle.
- the fan section includes a fan shaft driven by the epicyclic gear train and the oil collection feature is a portion of the fan shaft.
- the oil collection feature includes a first oil collection feature and a second oil collection feature.
- the first oil collection is the fan shaft and the second oil collection feature is an oil baffle.
- An epicyclic gear train for a turbine engine includes a plurality of intermediate gears, a carrier supporting the plurality of intermediate gears, a sun gear that meshes with the plurality of intermediate gears, and a ring gear surrounding and meshing with the plurality of intermediate gears the ring gear including first and second portions that each have an inner periphery with teeth.
- the first and second portions of the ring gear have an outer circumferential surface opposite the teeth that provides a first thickness, a second thickness greater than the first thickness and axially inward from the first thickness, and a flange extending radially away from said axis.
- the sun gear is rotatable in a first direction and the ring gear is rotatable in a second, opposite direction.
- epicyclic gear trains further includes an oil collection feature having an angled portion that is angled relative to the axis, and a radially aligned portion connected to the flange.
- the radially aligned portion further includes at least one groove operable to allow oil to pass through a connection between said radially aligned portion and said flange.
- the at least one groove is at less than or equal to a 45 degree angle relative to the flanges.
- the at least one groove is at an approximately zero degree angle relative to the flanges.
- the oil collection feature is an oil baffle.
- the oil collection feature includes a first oil collection feature and a second oil collection feature and the first oil collection is the fan shaft and the second oil collection feature is an oil baffle.
- a method of designing an epicyclic gear train for a turbine engine includes defining a carrier for supporting a plurality of intermediate gears, defining a sun gear for meshing engagement with the plurality of intermediate gears, and configuring a ring gear to surround and mesh with the plurality of intermediate gears.
- the ring gear is configured to include first and second portions that each have an inner periphery with teeth.
- An outer circumferential surface opposite the teeth provides a first thickness, a second thickness greater than the first thickness and axially inward from the first thickness.
- a flange extends radially away from said axis.
- any of the foregoing methods of designing an epicyclic gear train includes configuring the sun gear to be rotatable in a first direction and the ring gear to be rotatable in a second, opposite direction.
- the radially aligned portion is further configured to include at least one groove operable to allow oil to pass through a connection between the radially aligned portion and the flange.
- the oil collection feature includes a first oil collection feature and a second oil collection feature and the first oil collection is configured as part of a fan shaft and the second oil collection feature is an oil baffle.
- FIG. 1 is a partial cross-sectional view of a front portion of a gas turbine engine illustrating a turbo fan, epicyclic gear train and a compressor section.
- FIG. 2 is an enlarged cross-sectional view of the epicyclic gear train shown in FIG. 1 .
- FIG. 3 is an enlarged cross-sectional view of an example ring gear similar to the arrangement shown in FIG. 2 .
- FIG. 4 is a view of the ring gear shown in FIG. 3 viewed in a direction that faces the teeth of the ring gear in FIG. 3 .
- FIG. 1 A portion of a gas turbine engine 10 is shown schematically in FIG. 1 .
- the turbine engine 10 includes a fixed housing 12 that is constructed from numerous pieces secured to one another.
- a compressor section 14 having compressor hubs 16 with blades are driven by a turbine shaft 25 about an axis A.
- a turbo fan 18 is supported on a turbo fan shaft 20 that is driven by a compressor shaft 24 , which supports the compressor hubs 16 , through an epicyclic gear train 22 .
- the epicyclic gear train 22 is a star gear train.
- the epicyclic gear train 22 includes a sun gear 30 that is connected to the compressor shaft 24 , which provides rotational input, by a splined connection.
- a carrier 26 is fixed to the housing 12 by a torque frame 28 using fingers (not shown) known in the art.
- the carrier 26 supports star gears 32 using journal bearings 34 that are coupled to the sun gear 30 by meshed interfaces between the teeth of sun and star gears 30 , 32 .
- Multiple star gears 32 are arranged circumferentially about the sun gear 30 .
- Retainers 36 retain the journal bearings 34 to the carrier 26 .
- a ring gear 38 surrounds the carrier 26 and is coupled to the star gears 32 by meshed interfaces.
- the ring gear 38 which provides rotational output, is secured to the turbo fan shaft 20 by circumferentially arranged fastening elements, which are described in more detail below. Due to the use of the sun gear 30 in the described arrangement of the epicyclic gear train 22 , a worker of ordinary skill in the art would recognize that the sun gear 30 is rotatable in a first direction and the ring gear 38 is rotatable in a second, opposite direction.
- the ring gear 38 is a two-piece construction having first and second portions 40 , 42 .
- the first and second portions 40 , 42 abut one another at a radial interface 45 .
- a trough 41 separates oppositely angled teeth 43 (best shown in FIG. 4 ) on each of the first and second portions 40 , 42 .
- the arrangement of teeth 43 forces the first and second portions 40 , 42 toward one another at the radial interface 45 .
- the back side of the first and second portions 40 , 42 includes a generally S-shaped outer circumferential surface 47 that, coupled with a change in thickness, provides structural rigidity and resistance to overturning moments.
- the first and second portions 40 , 42 have a first thickness T 1 that is less than a second thickness T 2 arranged axially inwardly from the first thickness T 1 .
- the first and second portions 40 , 42 include facing recesses 44 that form an internal annular cavity 46 .
- the first and second portions 40 , 42 include flanges 51 that extend radially outward away from the teeth 43 .
- the turbo fan shaft 20 includes a radially outwardly extending flange 70 that is secured to the flanges 51 by circumferentially arranged bolts 52 and nuts 54 , which axially constrain and affix the turbo fan shaft 20 and ring gear 38 relative to one another.
- the spline ring is eliminated, which also reduces heat generated from windage and churning that resulted from the sharp edges and surface area of the splines.
- the turbo fan shaft 20 and ring gear 38 can be rotationally balanced with one another since radial movement resulting from the use of splines is eliminated.
- An oil baffle 68 is also secured to the flanges 51 , 70 and balanced with the assembly.
- the first and second portions 40 , 42 have grooves 48 at the radial interface 45 that form a hole 50 , which expels oil through the ring gear 38 to a gutter 60 that is secured to the carrier 26 with fasteners 61 ( FIG. 2 ).
- the direct radial flow path provided by the grooves 48 reduces windage and churning by avoiding the axial flow path change that existed with splines. That is, the oil had to flow radially and then axially to exit through the spline interface.
- the gutter 60 is constructed from a soft material such as aluminum so that the knife edges 58 , which are constructed from steel, can cut into the aluminum if they interfere.
- the seals 56 also include oil return passages 62 provided by first and second slots 64 in the seals 56 , which permit oil on either side of the ring gear 38 to drain into the gutter 60 .
- the first and second slots 64 , 66 are instead provided in the flange 70 and oil baffle 68 , respectively.
- oil used to cool and lubricate the epicyclic gear train 22 is heated and expelled from the epicyclic gear train 22 . Once expelled, the majority of the oil flows through the hole 50 along the oil flow path 100 , illustrated by the hollow arrows in FIG. 3 . A portion of the oil, however, escapes axially to either side of the first or second portion 40 , 42 .
- the heated oil has both a radial and a tangential velocity away from the axis.
- the radial velocity component causes the oil to be propelled radially outward and strike the angled (curved) portion of the turbofan shaft 20 , or the angled portion of the oil baffle 68 .
- the radial velocity component pushes the oil radially outward along the turbofan shaft 20 or the oil baffle 68 toward the flanges 70 , as illustrated by the secondary oil path 102 .
- the oil passes through grooves 104 in the turbofan shaft 20 or the oil baffle 68 , and through the first and second slots 64 in the seals.
- the grooves 104 are illustrated at a 0 degree angle relative to the adjacent flanges 70 , however it is understood that the angular velocity of the oil passing through the grooves 104 can be controlled by altering the angle of the grooves 104 up to a 45 degree angle, relative to the adjacent flanges 70 .
- the oil then drains into the gutter 60 .
- the tangential velocity of the oil causes the oil to continue to travel tangentially about the axis through the gutter 60 until the oil encounters a recollection feature that recollects the oil from the gutter 60 . In this way, the oil passes to the gutter 60 through a secondary oil collection feature in addition to passing through the hole 50 .
Abstract
Description
Claims (25)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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US14/293,279 US9115650B2 (en) | 2006-08-15 | 2014-06-02 | Ring gear mounting arrangement with oil scavenge scheme |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/504,220 US8753243B2 (en) | 2006-08-15 | 2006-08-15 | Ring gear mounting arrangement with oil scavenge scheme |
US13/437,442 US8764604B2 (en) | 2006-08-15 | 2012-04-02 | Ring gear mounting arrangement with oil scavenge scheme |
US13/484,579 US8740740B2 (en) | 2006-08-15 | 2012-05-31 | Ring gear mounting arrangement with oil scavenge scheme |
US14/293,279 US9115650B2 (en) | 2006-08-15 | 2014-06-02 | Ring gear mounting arrangement with oil scavenge scheme |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/484,579 Continuation US8740740B2 (en) | 2006-08-15 | 2012-05-31 | Ring gear mounting arrangement with oil scavenge scheme |
Publications (2)
Publication Number | Publication Date |
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US20140286755A1 US20140286755A1 (en) | 2014-09-25 |
US9115650B2 true US9115650B2 (en) | 2015-08-25 |
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Application Number | Title | Priority Date | Filing Date |
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US11/504,220 Active 2033-05-03 US8753243B2 (en) | 2006-08-15 | 2006-08-15 | Ring gear mounting arrangement with oil scavenge scheme |
US13/346,236 Abandoned US20120102971A1 (en) | 2006-08-15 | 2012-01-09 | Tapered bearings |
US13/437,442 Active US8764604B2 (en) | 2006-08-15 | 2012-04-02 | Ring gear mounting arrangement with oil scavenge scheme |
US13/484,818 Active US8795122B2 (en) | 2006-08-15 | 2012-05-31 | Tapered bearings |
US13/484,579 Active US8740740B2 (en) | 2006-08-15 | 2012-05-31 | Ring gear mounting arrangement with oil scavenge scheme |
US14/287,813 Active 2027-04-02 US9657572B2 (en) | 2006-08-15 | 2014-05-27 | Ring gear mounting arrangement with oil scavenge scheme |
US14/293,279 Active US9115650B2 (en) | 2006-08-15 | 2014-06-02 | Ring gear mounting arrangement with oil scavenge scheme |
US15/380,570 Abandoned US20170089448A1 (en) | 2006-08-15 | 2016-12-15 | Ring gear mounting arrangement with oil scavenge scheme |
US15/691,259 Active US9951860B2 (en) | 2006-08-15 | 2017-08-30 | Ring gear mounting arrangement with oil scavenge scheme |
US15/954,832 Active US10125858B2 (en) | 2006-08-15 | 2018-04-17 | Ring gear mounting arrangement with oil scavenge scheme |
US16/166,251 Active US10591047B2 (en) | 2006-08-15 | 2018-10-22 | Ring gear mounting arrangement with oil scavenge scheme |
US16/819,322 Active US10830334B2 (en) | 2006-08-15 | 2020-03-16 | Ring gear mounting arrangement with oil scavenge scheme |
US17/038,724 Active US11221066B2 (en) | 2006-08-15 | 2020-09-30 | Ring gear mounting arrangement with oil scavenge scheme |
US17/540,400 Active US11499624B2 (en) | 2006-08-15 | 2021-12-02 | Ring gear mounting arrangement with oil scavenge scheme |
Family Applications Before (6)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/504,220 Active 2033-05-03 US8753243B2 (en) | 2006-08-15 | 2006-08-15 | Ring gear mounting arrangement with oil scavenge scheme |
US13/346,236 Abandoned US20120102971A1 (en) | 2006-08-15 | 2012-01-09 | Tapered bearings |
US13/437,442 Active US8764604B2 (en) | 2006-08-15 | 2012-04-02 | Ring gear mounting arrangement with oil scavenge scheme |
US13/484,818 Active US8795122B2 (en) | 2006-08-15 | 2012-05-31 | Tapered bearings |
US13/484,579 Active US8740740B2 (en) | 2006-08-15 | 2012-05-31 | Ring gear mounting arrangement with oil scavenge scheme |
US14/287,813 Active 2027-04-02 US9657572B2 (en) | 2006-08-15 | 2014-05-27 | Ring gear mounting arrangement with oil scavenge scheme |
Family Applications After (7)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US15/380,570 Abandoned US20170089448A1 (en) | 2006-08-15 | 2016-12-15 | Ring gear mounting arrangement with oil scavenge scheme |
US15/691,259 Active US9951860B2 (en) | 2006-08-15 | 2017-08-30 | Ring gear mounting arrangement with oil scavenge scheme |
US15/954,832 Active US10125858B2 (en) | 2006-08-15 | 2018-04-17 | Ring gear mounting arrangement with oil scavenge scheme |
US16/166,251 Active US10591047B2 (en) | 2006-08-15 | 2018-10-22 | Ring gear mounting arrangement with oil scavenge scheme |
US16/819,322 Active US10830334B2 (en) | 2006-08-15 | 2020-03-16 | Ring gear mounting arrangement with oil scavenge scheme |
US17/038,724 Active US11221066B2 (en) | 2006-08-15 | 2020-09-30 | Ring gear mounting arrangement with oil scavenge scheme |
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US10830334B2 (en) | 2020-11-10 |
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US20120189430A1 (en) | 2012-07-26 |
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US20200278022A1 (en) | 2020-09-03 |
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US20180010681A1 (en) | 2018-01-11 |
US20180238437A1 (en) | 2018-08-23 |
US11221066B2 (en) | 2022-01-11 |
US20220243802A1 (en) | 2022-08-04 |
EP1890054A1 (en) | 2008-02-20 |
US20120102971A1 (en) | 2012-05-03 |
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US10591047B2 (en) | 2020-03-17 |
US20150252672A1 (en) | 2015-09-10 |
US20080044276A1 (en) | 2008-02-21 |
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